U.S. patent application number 16/739322 was filed with the patent office on 2020-07-23 for method for assembling an aircraft pylon.
This patent application is currently assigned to Airbus Operations S.A.S.. The applicant listed for this patent is Airbus Operations S.A.S. AIRBUS OPERATIONS LTD. Invention is credited to Audrey Benaben, Joel Dedieu, Thomas Deforet, Francois Martinel, Julien Moulis, Thierry Theron, Robert Whiffen.
Application Number | 20200231294 16/739322 |
Document ID | / |
Family ID | 67262452 |
Filed Date | 2020-07-23 |
United States Patent
Application |
20200231294 |
Kind Code |
A1 |
Martinel; Francois ; et
al. |
July 23, 2020 |
Method For Assembling An Aircraft Pylon
Abstract
A method for assembling an aircraft pylon having a primary
structure and at least one internal system at least partially
positioned within the primary structure, wherein the internal
system is positioned inside the primary structure before the last
lateral panel of the primary structure is attached. The absence of
one of the lateral panels facilitates the installation of the
internal systems.
Inventors: |
Martinel; Francois;
(Toulouse, FR) ; Dedieu; Joel; (Toulouse, FR)
; Theron; Thierry; (Toulouse, FR) ; Moulis;
Julien; (Toulouse, FR) ; Deforet; Thomas;
(Toulouse, FR) ; Benaben; Audrey; (Toulouse,
FR) ; Whiffen; Robert; (Bristol, GB) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Airbus Operations S.A.S.
AIRBUS OPERATIONS LTD |
Toulouse
Bristol |
|
FR
GB |
|
|
Assignee: |
Airbus Operations S.A.S.
Toulouse
FR
AIRBUS OPERATIONS LTD
Bristol
GB
|
Family ID: |
67262452 |
Appl. No.: |
16/739322 |
Filed: |
January 10, 2020 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64D 2027/262 20130101;
B64D 27/18 20130101; B64D 2027/264 20130101; B64D 27/26
20130101 |
International
Class: |
B64D 27/26 20060101
B64D027/26; B64D 27/18 20060101 B64D027/18 |
Foreign Application Data
Date |
Code |
Application Number |
Jan 21, 2019 |
FR |
19 00502 |
Claims
1. A method for assembling an aircraft pylon comprising a primary
structure, a secondary structure which surrounds the primary
structure, at least one internal system at least partially
positioned within the primary structure, and at least one external
system positioned outside the primary structure, the primary
structure comprising upper and lower spars, transverse frames
connecting the upper and lower spars and first and second lateral
panels arranged on either side of the transverse frames, wherein
the assembly method comprises, in chronological order: assembling
the primary structure with the exception of at least one of the
first and second lateral panels so as to obtain a primary structure
of which at least one lateral face is left open; installing the
internal system within the primary structure from the open lateral
face of the primary structure; and attaching one of the first or
second lateral panels so as to close each lateral face initially
left open.
2. The method for assembling an aircraft pylon according to claim
1, wherein only one of the first or second lateral panels is not
assembled at the end of the step of assembling the primary
structure.
Description
FIELD OF THE INVENTION
[0001] The present application relates to a method for assembling
an aircraft pylon.
BACKGROUND OF THE INVENTION
[0002] According to a configuration shown in FIGS. 1 and 2, an
aircraft 10 comprises multiple propulsion units 12 positioned below
the wing 14 of the aircraft 10.
[0003] A propulsion unit 12 comprises an engine 16, a nacelle (not
shown in FIG. 2) positioned around the engine 16, and a pylon 18
that provides the connection between the engine 16 and the wing 14.
The pylon 18 comprises a rigid primary structure 20 which, among
other things, serves to transmit forces between the engine 16 and
the rest of the aircraft 10, a secondary structure 22 which
encloses the primary structure 20 and reduces the drag of the pylon
18, and systems located inside and outside the primary structure
20. According to one configuration, the primary structure 20 is
connected to the engine 16 by an engine attachment 24 and to the
wing 14 by a wing attachment 26.
[0004] For the present application, a longitudinal direction X is a
direction parallel to the engine axis A16. A horizontal transverse
direction Y is a horizontal direction perpendicular to the engine
axis A16. A vertical transverse direction Z is a vertical direction
perpendicular to the engine axis A16. A vertical longitudinal plane
is a plane parallel to the longitudinal direction X and the
vertical transverse direction Z.
[0005] The terms "front" and "rear" ("Av" and "Ar" respectively)
refer to a direction of advance of the aircraft 10 that takes place
as a consequence of the thrust produced by the propulsion units 12,
this direction being represented by the arrow 28 in FIG. 1.
[0006] As shown in FIG. 3, the primary structure 20 comprises:
[0007] an upper spar 30, [0008] a lower spar 32, [0009] transverse
frames 34 which connect the upper and lower spars 30, 32, which are
arranged in transverse planes and which each have an approximately
square or rectangular contour, [0010] a front end wall 36 which
connects a front end of the upper spar 30 and a front end of the
lower spar 32, [0011] a rear end part 38 which connects a rear end
of the upper spar 30 and a rear end of the lower spar 32, [0012]
two lateral panels 40, 42 arranged on either side of the transverse
frames 34.
[0013] According to one assembly mode, the various elements of the
primary structure (the upper and lower spars 30, 32, the transverse
frames 34, the front end wall 36, the rear end part 38 and the
lateral panels 40, 42) are assembled so as to obtain a hollow box
with closed upper, lower and lateral faces. All that remains after
this assembly step is just small openings in the upper and lower
spars 30, 32 and in the lateral panels 40, 42, for access to the
interior of the primary structure 20.
[0014] After this, the systems are positioned within and without
the primary structure 20, then the secondary structure 22 is
installed.
[0015] According to this operating mode, accessibility for
installing the systems within the already-assembled primary
structure is limited, which can sometimes make the installation of
the systems long and complex for the operators.
BRIEF SUMMARY OF THE INVENTION
[0016] The present invention may remedy all or some of the
drawbacks of the prior art.
[0017] An aspect of the invention relates to a method for
assembling an aircraft pylon comprising a primary structure and at
least one internal system at least partially positioned within the
primary structure, the latter comprising upper and lower spars,
transverse frames connecting the upper and lower spars and first
and second lateral panels arranged on either side of the transverse
frames, characterized in that the assembly method comprises, in
chronological order, the steps of: [0018] assembling the primary
structure with the exception of at least one of the first and
second lateral panels so as to obtain a primary structure of which
at least one lateral face is left open, [0019] installing the
internal system within the primary structure from the open lateral
face of the primary structure, and [0020] attaching one of the
first or second lateral panels so as to close each lateral face
initially left open.
[0021] According to an aspect of the invention, the internal
systems are installed more easily, with better visibility for the
operators, which makes it possible to reduce the time taken for
installation.
[0022] According to another feature, only one of the first or
second lateral panels is not assembled at the end of the step of
assembling the primary structure.
BRIEF DESCRIPTION OF THE DRAWINGS
[0023] Other features and advantages will emerge from the following
description of the invention, which description is given solely by
way of example, with reference to the appended drawings in
which:
[0024] FIG. 1 is a side view of an aircraft,
[0025] FIG. 2 is a side view of a primary structure of a pylon
connecting an engine to a wing, illustrating one embodiment,
[0026] FIG. 3 is a perspective exploded view of a primary structure
of a pylon,
[0027] FIG. 4 is a side view of a partially assembled primary
structure of an aircraft pylon, prior to the installation of
internal systems positioned within the primary structure,
illustrating one embodiment of the invention,
[0028] FIG. 5 is a side view of the primary structure shown in FIG.
4, in which there are positioned internal systems, illustrating one
embodiment of the invention, and
[0029] FIG. 6 is a side view of the primary structure shown in FIG.
4, completely assembled.
DETAILED DESCRIPTION
[0030] FIGS. 4 to 6 show a primary structure 44 of an aircraft
pylon which comprises: [0031] an upper spar 46, [0032] a lower spar
48, [0033] transverse frames 50 which connect the upper and lower
spars 46, 48, which are arranged in transverse planes and which
each have an approximately square or rectangular contour, [0034] a
front end wall 52 which connects a front end of the upper spar 46
and a front end of the lower spar 48, [0035] a rear end part 54
which connects a rear end of the upper spar 46 and a rear end of
the lower spar 48, [0036] two lateral panels 56, 58 arranged on
either side of the transverse frames 50.
[0037] According to one embodiment, the primary structure 44
comprises upper and lower spars 46, 48, transverse frames 50
connecting the upper and lower spars 46, 48 and first and second
lateral panels 56, 58 that are arranged on either side of the
transverse frames 50.
[0038] The aircraft pylon also comprises at least one internal
system 60 positioned at least partially within the primary
structure 44, at least one external system positioned outside the
primary structure 44 and a secondary structure.
[0039] As illustrated in FIG. 5, according to one configuration the
aircraft pylon comprises multiple internal systems 60 such as pipes
62, cable bundles 62', a fire extinguishing system 62'', a drainage
system 62'''.
[0040] The elements forming the primary structure 44, the internal
and external systems and the secondary structure are not described
in greater detail since they will be known to a person skilled in
the art.
[0041] The method for assembling the aircraft pylon comprises a
first step of assembling the elements of the primary structure 44
with the exception of at least one of the first and second lateral
panels 56, 58. According to one operating mode, after the first
step only the first lateral panel 56 is not assembled.
[0042] After this first step, the upper and lower spars 46, 48, the
transverse frames 50, the front end wall 52, the rear end part 54
and the second lateral panel 58 are connected to one another by any
appropriate means such as welding, riveting, clinching, adhesive
bonding, bolting or other methods.
[0043] According to one operating mode, the various elements of the
primary structure 44 are pierced independently of one another prior
to assembly. They are bolted and/or riveted to one another.
[0044] This first assembly is not described in greater detail
because the upper and lower spars 46, 48, the transverse frames 50,
the front end wall 52, the rear end part 54 and the second lateral
panel 58 may be connected to one another in the same way as in the
methods of the prior art.
[0045] After this first step, the primary structure 44 forms a box
of which at least one lateral face 64, that which is ultimately
covered by the first lateral panel 56, is left open.
[0046] The method for assembling a pylon comprises a second step of
installing at least one internal system 60 within the primary
structure 44, from the open lateral face 64 of the primary
structure 44, in particular by introducing it via the lateral face
64. According to one operating mode, all of the internal systems 60
are positioned inside the primary structure 44 prior to mounting of
the first lateral panel 56.
[0047] The internal systems 60 are connected to one another and/or
to the primary structure 44 and/or to at least one external system
and/or to the secondary structure. These connections are not
described in greater detail since they are identical to those of
the prior art.
[0048] According to the invention, the internal system(s) 60 is/are
positioned inside the primary structure 44 before the last lateral
panel 56, 58 of the primary structure 44 is attached. In the
absence of one of the lateral panels 56, 58, the internal systems
60 are installed more easily, with better visibility for the
operators, which makes it possible to reduce the time taken for
installation.
[0049] After installation of at least one internal system 60, the
method for assembling the pylon comprises, for each initially open
lateral face 64, a step of attaching one of the first and second
lateral panels 56, 58 to the rest of the primary structure 44, in
particular to the upper and lower spars 46, 48, to the transverse
frames 50, to the front end wall 52 and/or to the rear end part 54
so as to close each initially open lateral face 64 and to thus
obtain a closed box shape as shown in FIG. 6.
[0050] Finally, the method for assembling the pylon also comprises
at least one step of installing the external systems and the
secondary structure.
[0051] According to one embodiment, the secondary structure
comprises multiple parts. At least one of these may be connected to
the primary structure 44 prior to the step of installing the
internal system(s) 60 or prior to the step of attaching the first
lateral panel 56.
[0052] At the end of the assembly method, the primary structure 44
may be identical to that of the prior art. The only difference is
the order of the steps of the assembly method.
[0053] While at least one exemplary embodiment of the present
invention(s) is disclosed herein, it should be understood that
modifications, substitutions and alternatives may be apparent to
one of ordinary skill in the art and can be made without departing
from the scope of this disclosure. This disclosure is intended to
cover any adaptations or variations of the exemplary embodiment(s).
In addition, in this disclosure, the terms "comprise" or
"comprising" do not exclude other elements or steps, the terms "a"
or "one" do not exclude a plural number, and the term "or" means
either or both. Furthermore, characteristics or steps which have
been described may also be used in combination with other
characteristics or steps and in any order unless the disclosure or
context suggests otherwise. This disclosure hereby incorporates by
reference the complete disclosure of any patent or application from
which it claims benefit or priority.
* * * * *